固体火箭冲压发动机导弹气动外形设计与试验研究

刘远, 程养民, 李晓晖, 闫宝任

刘远, 程养民, 李晓晖, 闫宝任. 固体火箭冲压发动机导弹气动外形设计与试验研究[J]. 空气动力学学报, 2016, 34(6): 790-796. DOI: 10.7638/kqdlxxb-2014.0043
引用本文: 刘远, 程养民, 李晓晖, 闫宝任. 固体火箭冲压发动机导弹气动外形设计与试验研究[J]. 空气动力学学报, 2016, 34(6): 790-796. DOI: 10.7638/kqdlxxb-2014.0043
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Liu Yuan, Cheng Yangmin, Li Xiaohui, Yan Baoren. Aerodynamic design and experimental study of a missile propelled by solid rocket ramjet[J]. ACTA AERODYNAMICA SINICA, 2016, 34(6): 790-796. DOI: 10.7638/kqdlxxb-2014.0043
Citation: Liu Yuan, Cheng Yangmin, Li Xiaohui, Yan Baoren. Aerodynamic design and experimental study of a missile propelled by solid rocket ramjet[J]. ACTA AERODYNAMICA SINICA, 2016, 34(6): 790-796. DOI: 10.7638/kqdlxxb-2014.0043
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固体火箭冲压发动机导弹气动外形设计与试验研究

  • 西安航天动力技术研究所, 陕西 西安 710025

详细信息
    作者简介:

    刘远(1991-),男,硕士研究生,主要研究方向:导弹武器系统工程设计.E-mail:steedliuy@163.com

  • 中图分类号: V211.7;E927

Aerodynamic design and experimental study of a missile propelled by solid rocket ramjet

  • Xi'an Institute of Aerospace Propulsion Technology, Xi'an 710025, China

摘要

    摘要
  • 摘要: 某固体火箭冲压发动机导弹存在着航程阻力大、静稳定性差、平衡攻角偏大、舵效偏高等一系列问题。根据导弹的基准外形，结合相关理论，对影响导弹气动性能的关键部件进行了分析与比较研究，并对外形进行改进，建立了一系列差异化几何模型。用FLUENT软件，对导弹在不同攻角条件下外流场进行数值计算，得出了各模型的轴向力系数、法向力系数和俯仰力矩系数随攻角的变化规律以及表面的压力分布情况。计算结果表明，就设计目标考虑，采用改进后的大进气道、小弹翼、舵面边条、后掠舵面和水平尾翼布局的模型性能最优。为进一步研究该最优布局下各关键部件对导弹气动性能产生的影响，进行了组拆选型风洞试验。试验中将这些关键部件逐步组装到光弹体上，前后共测试了16种模型状态，经对比分析，确定了气动性能最优的外形，且该最优外形与数值计算所确定的最优模型一致。随后对该最优气动外形的导弹进行全弹风洞测力试验。试验表明，相较于基准弹，优化后的导弹模型各项气动性能均有所提高，其中，轴向力系数数值减小了3%～4%，纵向焦点位置平均后移3%左右，平衡攻角较基准弹减小1.5°（60%）左右，对质心的俯仰舵效减小了40%左右，滚转舵效减小了35%左右。试验结果与同条件下的数值计算结果吻合较好，同时这也验证了导弹气动优化过程中CFD数值计算方法的合理性。
    Abstract: Many researches show that missiles propelled by ducted solid rocket ramjet is regarded superior at the aspects of firing range, velocity and maneuverability. To improve the unexpected defects of some solid fuel ramjet missiles, such as larger flight drag, poor static stability, larger trimming angle of attack and higher rudder effect, comparative studies of key components to the aerodynamic performance of the missile were fulfilled, a series of significant different models comparing to the basic missile configuration were established based on the aerodynamic characteristics of some components that exercise a major influence on the missile performance. Using the CFD software Fluent, the missile flow fields with different attack angles were simulated numerically, and corresponding axial force coefficient, normal force coefficient and pitching moment coefficient with variety of attack angels were obtained, the pressure distributing trend were analyzed. The results indicated that, in terms of the optimization target, configuration with larger size inlet, smaller wing, rudder surface of edge, sweepback rudder surface and horizontal tail is superior to others. To validate this analysis, an experiment were carried out in the FD-06 hypersonic wind tunnel. The key components were installed on the missile body step by step by building up method. Totally, 16 models were tested, and the test results indicated that the optimal shape showed the consistent with the optimal model obtained by CFD analysis. Comparing to the basic missile, various performances of the optimized model were improved obviously under the studied conditions, the axial force coefficient decreased about 3.0%~4.0%, the longitudinal focus position moved backwards about 3.0% and the balance angle of attack decreased about 1.5°(60%), and the pitching and rolling rudder effect reduced 40% and 35% respectively. Furthermore, CFD results agreed well with the test results, and the reasonableness of CFD numerical methods instead of tunnel test results in the process of aerodynamic optimization were verified.
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出版历程
  • 收稿日期:  2014-05-26
  • 修回日期:  2016-05-17
  • 网络出版日期:  2021-01-07
  • 刊出日期:  2016-12-24

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